Beechcraft E18

During arrival at night in fog and drizzle, the pilot was cleared for an ILS runway 1l approach. While on the approach, she reported encountering moderate rime ice. Radar data showed that the airplane continued inbound on the localizer until it neared the middle marker, then it deviated about 20° left and collided with the ground, about 300 feet short and 300 feet left of the threshold. According to witnesses, the airplane stopped its descent and slowed down, shortly before entering a steep descent and a spin. An on-scene investigation revealed no preimpact airframe, control system, or powerplant anomalies. The wings had 1/4 inch of ice on the leading edge and a 1/2 inch high ridge of ice, parallel to the deicing boots, about 3 inches aft of the boots. The cockpit and windshield heating system were found in the 'off' position. The pilot's logbook was not available for inspection. Company records showed she had passed a 14 cfr part 135 checkride on may 20, 1994. The faa checkride form was administered and signed by the chief pilot. However, other records/information showed the chief pilot would not have been able to have given the checkride on that date.

The pilot was conducting his initial revenue and solo flight for this company, in this type of airplane. The weather for takeoff included fog and low ceilings. The airplane was equipped with a primary (left) attitude indicator which was electrically operated via an independent switch. This aircraft was the only such airplane operated by this company, with an independent switch configuration for the primary attitude indicator. The airplane collided with the terrain on the airport, just after takeoff. Subsequent examination revealed no anomalies with the engines or airframe. The primary attitude indicator was located. On examination it was found to have a malfunctioning on/off flag which gave the indication of being operative regardless of power to the unit. No rotational damage was noted within the gyro housing. The pilot, sole on board, was killed.

The pilot of a twin-engine cargo airplane shut down the left engine and feathered the propeller due to a loss of engine oil. The FAA ARTCC handling the flight vectored the airplane toward a VOR. Due to the airplane's altitude and distance from the center's radar, the pilot of the airplane had to perform a full instrument approach procedure. The airplane maintained its enroute assigned altitude until passing the VOR outbound. Ntap readouts show the airplane descending throughout the procedure turn and inbound leg of the approach. The airplane's last radar contact was 300 feet below the inbound altitude for the approach while outside the final approach fix. The airplane collided with trees and terrain approximately 2 1/4 miles from the airport. The VOR is 5.5 miles from the airport. The on-scene investigation revealed the left engine's propeller had been feathered, its number nine cylinder mounting studs on the engine's case were crushed downward or were broken off at the case's surface, and the landing gear had been extended. The pilot, sole on board, was killed.

The instrument rated pilot was en route to pick up cargo. He received three preflight weather briefings earlier that indicated snow, mountain obscuration, and low visibility. He reported, 'seeing the lights of university,' and requested a contact approach. He also said that if he could not get in, he would make an ils approach. When the airplane was 4 miles south of the airport, the New York air traffic controller cleared the pilot for a contact approach to runway 24. A witness reported hearing a low flying airplane. He stated that it was snowing heavily and he saw the tail light of an airplane briefly through the snow. He also reported that a snow squall was in the area at the time. Shortly afterward, he heard what was later determined to be the sound of the collision. Search personnel located the wreckage 3.3 miles south of the airport on top of mount nittany which was about 2000 feet high. The pilot, sole on board, was killed.

During the air tour flight the pilot had radioed his intentions to FSS to overfly an area about 5 miles southwest of the island of Maui. Approximately 10 minutes later the airplane impacted mountainous terrain on the island. IMC prevailed at the time and location of the accident. The pilot did not possess the minimum hours stipulated in the company ops manual to qualify as a captain. He falsified the employment application and resume. The company did not pursue substantive pre employment background checks, nor were they required by the FAA to do so. Regulations are needed for air tour operators that will enable FAA inspectors to require, rather than merely encourage, operators to adhere to procedures that offer the safety improvements of sfar 50-2 and FAA handbook 8400.10 bulletin 92-01. All nine occupants were killed.

On approach to Island Lake Airport (Stevenson Island), the twin engine aircraft struck the surface of a frozen lake and crashed near Garden Hill. The pilot was slightly injured and the aircraft was damaged beyond repair.

After takeoff at 600 feet, the right engine quit. The pilot said, '[the] altitude dropped about 100 feet and airspeed at 120 knots. The right engine came back again . . . It ran for about 10 seconds. [I] adjusted power on left engine . . . Feathered right prop and tried to maintain altitude, but airspeed kept diminishing, so I had to descend to maintain airspeed.' The pilot put the landing gear down to absorb the shock of landing in a field. An examination revealed no malfunctions in the engine or carburetor. The airplane was within allowable gross weight and center of gravity limits. The weather was: ceiling 600 feet broken, 1,500 feet overcast, visibility 3 miles, light rain and fog. The pilot escaped with minor injuries and the aircraft was damaged beyond repair.

Crashed in unknown circumstances in the sea shortly after takeoff from Masbate Airport. Occupant fate remains unknown.

The right engine lost power during the initial climb after lift-off. A witness heard a noise and observed flames coming from the right engine cowling as the airplane climbed. The airplane entered a turn after climbing about 200 feet, descended through a small grove of trees, crashed in a pasture, and burned. During takeoff, the plane's gross weight was about 11,050 lbs and the cg was behind the aft limit. Its maximum certified weight limit was 9,700 lbs. The pilot was aware of a gross weight problem before takeoff. An exam revealed evidence that the left engine propeller was in the feathered position and the right propeller was not feathered at impact. A check of the right engine disclosed that the n°3 cylinder intake valve had failed from fatigue. The pilot, sole on board, was killed.

Shortly after departing from runway 15L at the Baltimore-Washington Intl Airport, the pilot transmitted that he had an emergency consisting of a fire under his side panel. He reported he was going to circle and land. According to witnesses, flames and smoke were in the cockpit area. The aircraft started a gradual descent during a left turn. Subsequently, it crashed into a house. An examination of the wreckage did not reveal the origin of the fire; however, a CB radio was found with evidence that it may have been wired to the aircraft electrical system. The owners stated that the CB was not installed in the aircraft prior to the pilot's use of the plane on that flight. The pilot, sole on board, was killed.